Toy airplane



M. PALMER.

TOY AIRPLANE.

1,412,418. APPLICATION ELLED, JAN.27, 1922- Apr 11,

2 SHhETSSHEET I.

E9 La:

W zawumtoz w'aim UNITED "STATES PATENT OFFICE.

CMIONTAGUE PALMER, OF TENAFLY, NEW JERSEY.

or AIRPLANE.

- Specification of Letters latent. Patented A111. 11, 1922- Applicationfiled January 27, 1922. Serial No. 532,348.

To all whom it my concerns for use, and disassembled for packing andtransportation. X

. My lnventlon is characterized in one of its features by. having afuselage which is built up of four longrons which are to be assembled,in spaced, quadrilateral form, and united by means of a series ofrectangular bulkheads, composed of thin sheet metal lic material.

The longrons are respectively provided with opposite slits orincisionsat predetermined points in their length, for the embedmenttherein of the bulkheads, at their respective corners, to thus serve aslocalizing means in the longitudinally'spaced arrangement of thebulkheads relatively to the fuselage. The bulkheads also have free endport-ions or tabs that are capable of folding over upon the-longrons tosecurely unite these parts. v I

'A further feature of invention comprehends the wing construction, whichineludes ribs of thin sheet metallic material, flanged at their u perand lower edges t increase'their rigi ity, and apertured to receive thebeams, which latter-are provided with slits or incisions atpredetermined points in their 'length for the-embedment therein of theribs, to thus serve as localiz-i ing means. The ribs are symmetrical intheir chordwise curvature to be capable of interchangeable employment.Sheathing for the fuselage also comprises a feature of my invention,with spacedyelements extendingtransversely, thereof, which also serve asguides for the wing beamsand as means for securing the sheathing to thefuselage framework.

Other features and advantages of my invention will hereinafter-appear.

In the drawings Figure 1 is a top plan view of a toy airplane'embodyingmy improvements.

Fig. 2 is an enlargedsection on the line.

2-2 of Fig. 1 showing a bulkhead in end View thereof.

Fig. 3 is. a similar section on the line 3 3 of Fig. 1 showing thespacermeans for the fuselage sheathing.

Fig. 4 is a side elevation, part-1y broker. away, of my toy airplane.

Fig. 5 is a perspective elevation of the radiator.

Fig. 6 is a perspective elevation of the fuselage front end.

Fig. 7 is a section on the line 7 of Fig. 6.

Fig. 8 is a perspective elevation of the fuselage rear end.

Fig. 9 is a fragmentary side elevation of a wing rib.

' Fig. 10 is a detail of an anchorage fitting for the tension wires, andFig. 11 is a detail view showing the means of connecting the verticalrudder to the rear fitting.

The fuselage or body portion of my improved toy airplane is composed ofthe four longrons 1, arranged in quadrature, and engaged, respectively,at the corners of a series of bulkheads 2, which are disposedtransversely of the structure. are composed of thin sheet metallicmaterial, and are of open or frame-like character, the outer edgebeingformed into a right angular flange 3 to imparta degree of stiffnessor rigidity to the structure. At the respective corners of the bulkheadsrectangular recesses 4 are provided for the reception of the longrons 1,extended portions or tabs 5 of the flange S being adapted to fold overupon the longrons, to clamp them into engagement with the bulkheads.Also the longrons are each rovided upon res ective inner sides thereoiin entations 6, for the reception of outer edge portions of thebulkheads, to localize the bulkheads, relatively to the longrons,lengthwise of the latter. c

One of the purposes of my invention is to provide for the production ofall the separate elements necessary in the construction of a toyairplane in such manner that these elements may be easily put togetherwith expedition and accuracy and securely united in the ultimatestructural form, with- The bulkheads 2 with slits or itself serves asaforward end abutment for the longrons.

The plate 7 has lugs 9 struck therefrom and projected outwardly, and .anelement 10, shaped to resemble a radiator, and adapted to fit over plate7, has apertures 11 for the reception of lugs 9, which may be bent over,outside element 10, to clinch it to plate 7 A rear fitting 12, composedof sheet metallic material, is shaped to provide the upper and lowerchannel portions 13, 14, for the reception respectively, of theconverged ends of the upper and lower pairs of longrons, while thematerial of fitting 12, at opposite sides thereof, is bent inwardly tocomprise a spacer 15 separating the upper and lower longrons. It will beappreciated, in this structural form of fitting 12, that its rear wallserves as a terminal abutment for the longron ends.

Sheathing 16, in the form of a thin sheet of metallic material, isfitted over the top and sides of the frame, at its forward por tion,including a representation of a cockpit and engine housing. The rearwardedge of sheathing 16, is adapted to be inserted between the longrons andthe flange 3 of one of thebulkheads 2, to connectit with the frame, saidsheathing also having tabs 17 at its forward side edges, to foldunderthe lower longrons.

Furthermeans of securing the sheathing to the frame comprises the pairsof plates 18, with bolts 19, the plates of a pair lymg respectivelyoutside the sheathing and against the inner surface of an adj acentlongron, the union beingeffected by engaging the plates .18 with bolts19 which extend respectively across the u per and lower surfaces of alongron, t e upper bolt belng passed through an orifice providedtherefor in the sheathing.

Spacer devices for the sheathing, which, as will be hereinafterdescribed, also serve as anchorage for the wing beams, consist of hollowmembers 21 produced by folding thin sheet metallic -material intorectangular form, with end extensions 22 adapted to project outwardlythrough rectangular ori- 'fices 23 provided in the side walls ofsheathlocalize he spacers between said walls Also the spacershaveshoulder portions 23 that lie close up against the inner surfaces ofthe respective walls, thereby enabling the spacers to serve ascompression members, to prevent the collapse of the sheathing w(alls. I

The wings, generally indicated by the reference character 24, arecomposed of the beams '25, which are rectangular in 'crosssection, andprovided with transverse slits 26 at various points along their length.

Ribs, 27, formed of thin sheet metallic material, and provided withupper and lower flanges, 28, 28*, respectively, to accord them astiffening channel-like section, each has rectangular orifices 29 in itsweb portion to receive the beams. The webs of the rib members, at theupper portions of the orifices 29, are adapted to enter the slits 26 inthe beams, and tabs 30 cut out from the lower portions of'the orifices 29, are adapted to be folded up against the bases of the beams to therebysecure them in their engagement with the ribs. ,By these means the ribsare localized in set positions relatively to. the beams. Y

The ribs are provided with symmetrical curvatures toward opposite endsin order that the ribs may be used interchangeably with wings at eitherside of the fuselage, the curvatures at the upper surfaces of the ribsmeeting the straight plane base thereof, .and, at the respective ends ofthe ribs, where the flanges 28, 28 come together, are pro- ,vided withmeans for the reception ofa wire 31 which extends around the perimeterof the wing. The wire has its opposite ends engaged in apertures 32provided upon a rib lying next the fuselage, a wire 31 extendingtherefrom continuously about the wing and lying in end recesses providedat outer terminal points of the beams,'whereby there is produced acompact wing frame structure.

The beams project beyond the'ribs which lie next the fuselage, and theprojecting porti ons of the beams are adapted to enter the hollowmembers 21 which serve as sheathing spacers; said beam ends, for theopposite wings, having abutting relation within 1-15 the spacers, bywhich they are mounted in the assembled positions of the wings.

I Tension wires 33, provided for. the pur pose of securing the wingstqthe fusela e,

and stiffening the union between these e ements," are secured inposition as follows A bifurcated mast cJInPOSBd of a strip of \thinsheet metallic material folded upon itself to'constitute its upper end,and provided with the legs 34, is adapted to straddle the fuselage, overthe sheathing 16, and directly above the openingor clearance 35 ,whichisIrepresentativeofa cock-pit, theoping 16, and to beturned overagainstthe' posite ends of these legs lying against;the

outer surfac'es of the respective walls, to 1' esp'ectiveopposite outer"surfaces of the '130 sheathing. The legs are secured to the fuselage bymeans of pairs of clamping grons, and to lap over the upper surfacethereof, as indicated at 41, whereby this strip 39 also serves as areinforcing spacer member for the longrons of the frame structure.

I have devised a special form of fitting for engagement with a rib uponeach of the wings to comprise anchorages for the outer ends of thetension wires 33, 38. These fittings, (see detail view, Fig. 10) consisteach of thin sheet metallic material shaped to comprise thesocketportion 42, to fit over the lower rib portion; the socket portion43 to straddle a beam, the upper, forwardly inclined portion 44 with anengaging orifice for an upper wire, and an inwardly extend-.

ed lower portion 45 with engaging means for a lower tension wire.

One of these fittings is applied to each beam of the wing, and therespective tension wires, when strung between the fittings and the mastand between the fittings and the lower anchorage eyelets 40, serve tosecure the wings to the fuselage with suitable tension.

The landing gear is composed of V-shaped hangers 46, disposed atopposite sides of the fuselage and secured at their upper ends theretoas by the fastening means 18, the axle 48 carrying the wheels 49, beingmounten in the lower ends of the hangers.

The propeller, 50,carried by a spindle 51, is mounted thereby inabearing 52 provided on the radiator, said spindle having a terminalhook 53 for engagement by a power member 54, whoseother end isengageable with a hook 55, carried by a plate 56 that is fittedtransversely of the fuselage, toward its rear end. The plate 56 has arearwardly extended, upper flange 571 which is adapted for the receptionof the forward edge of the rear wing or elevator 58, to localize it. inits set position upon the rear of the fuselage.

v The vertical rudder 59, whose forward, lower edge 60 abuts against therear surface of fitting 12, overhangs the rear surface portion ofelevator 58, to secure the latter upon the fuselage; and said rudder hasat its edge 60 a pair of plate like fingers 61 which are adapted to bepassed through a slit 62 in fitting12 and to be bent over against theinner heads.

surface of the fitting, to secure the rudder thereto.

Variations within the spirit and scope of my invention are equallycomprehended by the foregoing disclosure I claim 1. The combination, ina toy airplane, of a fuselage composed of spaced longrons, andbulkheads, of sheet material disposed transversely thereof, the longronshaving slits for the edgewise localizing engagement of the bulkheads.

2. The combination, in a toy airplane, of a fuselage composed of'spacedlongrons, and bulkheads of sheet metallic material disposed transverselythereof, the longrons having slits for the edgewise localizingengagement of the bulkheads, andthe bulkheads having projcting portionsto engagingly fold over upon the longrons.

3. The combination, in a toy airplane, of a fuselage composed of fourlongrons arranged in spaced quadrature, and bulkheads 'of flanged sheetmetallic material disposed transversely thereof, the bulkheads havingcorner recesses for the reception of the respective longrons, andprojecting portions to engagingly fold over upon the longrons, and thelongrons having slits for the ed ewise,.localizing engagement of the buk- 4. The combination, in a toy airplane, of a wing therefor having abeam with a transverse slit, and a rib composed of flanged sheetmetallic mate-rial, its web having an orifice to receive the beam, theslit in the beam serving to localizingly engage the rib, edgwise, at itsorifice, and the rib having a cut away portion at its orifice tosecuringly fold against the beam.

5. The combination, .in a toy airplane, of a wing therefor havingparallel beams, each with transverse slits, and a series of ribscomposed each of flanged, sheet metallic material, their webs havingaligned orifices, to receive the respective beams, the slits in thebeams serving to localizingly engage the ribs, edgewise, at theirorifices, and the ribs having cut away portions at their orifices tosecuringly fold against the beams.

6. The combination,'in a toy airplane, of a fuselage composed oflongrons arranged in quadrature, sheathing therefor provided withopposite apertures in its side walls, a tubular member composed offolded sheet metallic material extended between the side walls andserving for the reception of opposite, wing beams, the tubular membershaving shoulders to engage the inner surfaces of the sheathing walls,and end projections to clinch against the outer surfaces thereof.

7. The combination, in a toy airplane having a fuselage composed ofupper and lower with beams and transverse ribs, of a bifurcatedmast'extending from and secured to the upper longrons of the fuselage,and a transverse compression member extended between the lower longronsof the fuselage,

the compression member having terminal projecting'portions, fittingsengageable with the Wings, and tension wires extended respectivelybetween the mast and fittings and between the projecting port-ions ofthe compression member and the fittings.

8. The combination, in a toy alrplane having a fuselage composed oflongrons, of a I Signed at New York in the county and State .of New Yorkthis 24th day of January, 1922.

' MONTAGUE PALlWER.

